CN1098491A - The stabilizer of gas-turbine combustion chamber and the gas turbine that stabilizer is housed - Google Patents

The stabilizer of gas-turbine combustion chamber and the gas turbine that stabilizer is housed Download PDF

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Publication number
CN1098491A
CN1098491A CN94104611A CN94104611A CN1098491A CN 1098491 A CN1098491 A CN 1098491A CN 94104611 A CN94104611 A CN 94104611A CN 94104611 A CN94104611 A CN 94104611A CN 1098491 A CN1098491 A CN 1098491A
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China
Prior art keywords
stabilizer
gas
combustion
fuel
temperature
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CN94104611A
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Chinese (zh)
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CN1128951C (en
Inventor
伊藤和行
村上忠孝
川池和彦
小豆畑茂
黑田伦夫
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Hitachi Ltd
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Hitachi Ltd
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Priority claimed from JP5080613A external-priority patent/JP2798338B2/en
Priority claimed from JP23339393A external-priority patent/JP2860234B2/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
    • F23N5/242—Preventing development of abnormal or undesired conditions, i.e. safety arrangements using electronic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2241/00—Applications
    • F23N2241/20—Gas turbines

Abstract

Comprise that one is provided with to help with the surface except that the heat absorption surface that contacts with combustion gas of the stabilizer of combustion gas stabilized contact device part and the supporting portion that is used for rectification and disturbs device, the transmission of heat of from the stabilizer to the air fuel, flowing with raising.The most close heat absorption surface help the distance of disturbing between device and the heat absorption surface to be at least describedly to help 4 times that disturb device, to prevent owing to be provided with to help and disturb the backfire that device causes.

Description

The stabilizer of gas-turbine combustion chamber and the gas turbine that stabilizer is housed
The present invention relates to gas-turbine combustion chamber stabilizer and the gas-turbine combustion chamber that is equipped with stabilizer.Be particularly related to the operating range that to widen gas-turbine combustion chamber to guarantee smooth combustion and to reduce the stabilizer of the infringement that causes by high-temperature fuel gas and be equipped with the gas-turbine combustion chamber of this stabilizer.
In addition, the present invention relates to the method for combustion condition that each firing chamber of premixed combustion is wherein carried out in a kind of detection, and relate to one and carry out the system of this method and the controller of a combustion chamber equipment.
The line stabilization burning keeps flame in gas-turbine combustion chamber the time, and promptly the steady flame is very important.Use stabilizer to guaranteeing that this operation is very effective.This stabilizer of some types is disclosed, for example, Japanese Patent Application Publication No.115624/1982 relates to a kind of stabilizer (V-shaped groove) of V font, it has the well-mixed winglet of wake flow that is used to make in the generation of the downstream side of V-shaped groove, Japanese Patent Application Publication No.210721/1989 relates to the method for stabilizer of channel shape cross-section that a kind of connection has the V-arrangement of simplification, and U.S. Patent No. 3736746 relates to the position of placing stabilizer.
Gas turbine needs to operate in the wide output area corresponding to a big load variations.For the gas turbine of power station type, it must stand the long-time continuous running.Thereby the gas-turbine combustion chamber stabilizer must have the stable combustion condition and the performance that prevents to be out of shape and to break owing to heat of maintenance in the operational condition scope.Specifically, even stabilizer must be when making operational condition change owing to load variations etc., also can prevent rough burning, accidental ignition for example, backfire, the generation of burning swing etc., in addition, because stabilizer is exposed in the high-temperature combustion gas on the one hand, be exposed on the other hand in the air and fuel gas that flows in the firing chamber, the maximum temperature of stabilizer must be controlled in the scope that can both accept for every kind of part material, and its structure also must be able to be suppressed at the superhigh temperature stress that produces on its local location simultaneously.Yet conventional gas-turbine combustion chamber stabilizer can't satisfy these requirements.
In addition, the combustion condition in the control firing chamber is to reduce waste gas NO xWith the burning gas temperature that makes the combustor exit place evenly to prevent that gas turbine blades overload from being very important.Combustion chambers burn condition control technique is disclosed in, for example, Japanese Patent Application Publication No.218535/1985, No.135942/1986 is among No.49136/1986 and the No.29626/1989.This technology roughly is divided into two kinds, and the fuel quantity of the burning gas temperature control ejection that a kind of basis is surveyed at the combustor exit place is another kind of according to the NO that records at the combustor exit place xThe fuel quantity of concentration control ejection.
Except that above-mentioned technology, a kind of technology is also disclosed, it uses from fuel quantity of the visual processing technique control ejection of taking that is formed at the flame picture the main combustion chamber or the like.
First purpose of the present invention provides a kind of gas-turbine combustion chamber stabilizer that satisfies above-mentioned two requirements,, provides a kind of gas-turbine combustion chamber stabilizer that is, and it can improve combustion stability, and prevents the undue rising of various component materials temperature.
Second purpose of the present invention provides a kind of combustion stability with improvement and gas turbine engine of the gas-turbine combustion chamber in life-span of being equipped with, gas turbine power station, or utilize the industrial waste heat system.
A further object of the present invention provides a kind of method that accurately detects combustion condition, the controller of the combustion condition control combustion chamber equipment that a kind of system that carries out this method and basis are recorded by said method.
In recent years, gas-turbine combustion chamber has the trend that adopts premixed combustion, because premixed combustion can reduce waste gas NO xAmount.Premixed combustion is reducing waste gas NO xThe aspect is better than diffusive combustion, but is not so good as diffusive combustion aspect combustion stability.The firing chamber why Here it is respectively is used for premixed combustion all is provided with stabilizer at premix burner, or design makes and forms eddy current to stablize premixed combustion flame in the firing chamber.
Basically we can say the burning gas temperature and the NO that record at burner outlet in the prior art xCertain relation is arranged between concentration and the combustion condition, yet, if stabilizer is set in the premixed combustion chamber or in the firing chamber, forms eddy current, the burning gas temperature at combustor exit place or NO xConcentration always can accurately not indicate the combustion condition at upstream side, and in addition, infeeding air of being used for cooling combustion chamber material and dilute combustion gas in the firing chamber or the like becomes these combustion gas and NO at the combustor exit place xA factor of the non-accurate indication of concentration.For avoiding this problem, directly the temperature with thermometer measure flame self is considered to an effective method.Yet, also do not have a kind of thermometer that can measure the very high temperature of flame so far.Even this thermometer is arranged, also be disadvantageous with the temperature of thermometer measure flame, because thermometer self will disturb flame, in this unsettled flame, can not accurately measure flame temperature.
If judge combustion condition with flame picture, the problems referred to above can not take place then, this is because direct observed object flame.Even now, it is difficult accurately focusing on flame, because flame is expanded in the space and beated.According to different observed directions, flame is overlapped, can not only absorb the image of target flame in many cases.
In other words, prior art can not accurately detect combustion condition.
Usually, stabilizer is by making the combustion gas circulation that is formed at the stabilizer afterbody and the steady flame.Fuel and air with process that combustion gas mix in and burn.Owing to catch fire for example accidentally, backfire, the rough burning of fuel swing or the like causes by burner structure and operational condition, thereby to improve combustion condition at large be difficult.
By scrutinizing the combustion process of gas-turbine combustion chamber, the present inventor has found that be very important by regulating mixed process finishing the present invention around place smooth combustion reaction pair of starting of stabilizer.
In the present invention, a kind of method of device as adjusting mixed process of disturbing that help is set on the surface except that the combustion gas area of heating surface of stabilizer.
In addition, in the present invention, on the surface except that the combustion gas area of heating surface of stabilizer, be provided with many helping and disturb device, be made as 4 times that help the height of disturbing device at least thereby disturb distance between the device and the area of heating surface near helping of the area of heating surface.
Best, be used for stabilizer of the present invention and comprise a stabilizer part and a supporting portion.Stabilizer part and supporting portion should be as a whole, and angle between the two is between 120 ° to 160 ° simultaneously.Helping the height of disturbing device is 0.1mm to 1mm.
When the gas-turbine combustion chamber that stabilizer of the present invention is housed with is used for a gas turbine powered generator, when a gas turbine power station or an industrial waste heat utilize system, will realize second purpose of the present invention.
Help when disturbing device when being provided with on the surface except that the combustion gas contact surface at stabilizer, to disturb by helping that flow air and fuel form little vortex after the device each these.This will break each thermal boundary layer, and its result has improved thermal conductivity and quickened transmission of heat from the stabilizer of relatively-high temperature to flow air and fuel around stabilizer.Usually, the temperature of air and fuel stream is 200 to 400 ℃, and the temperature of stabilizer is 500 to 800 ℃.When the transmission of heat between them was quickened, the temperature of air and fuel rose, and made it be easy to start burning in mixed process, and the temperature of air and fuel stream is higher in mixed process.Thereby can make burning more stable.In addition, also the temperature to reduction stabilizer self is effective to quicken transmission of heat.
Usually, help 4 times that disturb the device height by helping the length of disturbing the eddy current that device forms to be about.When this eddy current arrives area of heating surface, flame probably backfire to the upstream side of the stabilizer area of heating surface, make distance that helping of the most close area of heating surface disturb between the device and the area of heating surface greater than help 4 times of disturbing the device height can reduce this may.
Load variations in the gas-turbine combustion chamber can greatly be disturbed air and fuel stream.In a kind of so disturbed air stream, helping and disturbing device is not very effective for transmission of heat.Yet, even in this disturbed air stream, disturb device if having the stabilizer part of a combustion gas area of heating surface and be arranged to be provided with to help on the surface of the dirty supporting portion of stabilizer part in comprising of stabilizer, still can improve transmission of heat.In other words, the supporting portion of stabilizer should be arranged at the upstream of stabilizer part, thereby is assigned to weaken the interference of air stream by support.Thereby, can not cross and disturb greatly that stabilizer is lip-deep to help the transmission of heat of disturbing device from being arranged at.If stabilizer part and supporting portion in conjunction with an integral body, will more steady from hot flame stabilizer part to the transmission of heat of relatively low supporting portion then.
If stabilizer part and supporting portion is combined as a whole and the angular setting between them between 120 ° to 160 °, then can make from the stabilizer to the air and the transmission of heat of fuel stream more perfect.In other words, if the angular setting between stabilizer part and primary air and the fuel stream is 120 ° or littler, then less relatively and disturb transmission of heat near the air velocity of stabilizer part surface.If above-mentioned angle is 160 ° or bigger, then heat conducting resistance to heat increases, thereby has hindered from the next transmission of heat in stabilizer surface.Yet,, all can obtain good balance in the transmission of heat of stabilizer part and supporting portion if the angle between stabilizer part and the supporting portion is 120 ° to 160 ° as described herein.This will make the transmission of heat between stabilizer and air and the fuel gas reach best.
Help and disturb device and be used for by thereafter fluid produces eddy current and transmission of heat is quickened in very little drift being formed at.If helping the height setting of disturbing device is 1mm or bigger, then produce eddy current and drift on a large scale, weaken and help the effect of disturbing device.In addition, be 0.1mm or littler if help the height setting of disturbing device, will can not produce effective disturbance.Thereby, help the height of disturbing device should be as described herein to remain on high level will help the heat-conductive characteristic of disturbing device by 0.1mm to 1mm.
When in gas-turbine combustion chamber, stabilizer being set, can improve gas turbine engine, gas turbine power station, or utilize the reliability and the life-span of industrial waste heat system.
According to of the present invention, can quicken the temperature that the transmission of heat from the gas-turbine combustion chamber stabilizer to fuel that centers on this stabilizer and air stream is flowed with increase air and fuel, and the temperature that reduces stabilizer.Its result can improve combustion stability, and the temperature of protection stabilizer can be its local undue rising.
The gas-turbine combustion chamber that is equipped with stabilizer of the present invention by outfit can provide the gas turbine engine that combustion stability improves and the life-span increases, gas turbine power station or utilize the industrial waste heat system.
Be the combustion condition detecting method that realizes the object of the invention below.
The method of the detection combustion condition of firing chamber is characterised in that the relation that at first detects between stabilizer temperature and the premixed combustion gas condition, measure the temperature of stabilizer then, and according to stabilizer temperature that has recorded and above-mentioned relation detection combustion condition, above-mentioned firing chamber has the fuel that premix burner mixes with ejection and the premixed gas of air, with a stabilizer, be used for forming a circular flow, with the stable flame that forms by the burning premixed gas by the combustion gas of burning premixed gas generation in its downstream side.
Specifically; the above-mentioned relation relevant with the combustion condition detecting method is considered to a kind of temperature according to stabilizer, and whether to indicate combustion condition in the stabilizer temperature range that presets be normal or unusual relation; or the relation of the relation between a kind of air-fuel ratio of indicating stabilizer temperature and premixed gas, or NO in a kind of stabilizer temperature and the combustion gas xRelation between the concentration, or the like.
(this system is used to have the fuel of an ejection premix and the premix burner of air gas to the combustion condition detection system that achieves the above object, with the firing chamber of a stabilizer, stabilizer forms the circulation of combustion gas that produced by the burning premixed gas with the stable flame that is formed by the burning premixed gas in its downstream side) be characterised in that device with a temperature that is used to measure stabilizer and one are used for the device that relation between the combustion condition of the preset temperature of temperature that basis records by the stabilizer temperature measuring equipment and stabilizer and premixed gas detects combustion condition.
Here the combustion condition detection system of mentioning should preferably have a device that is used to show the combustion condition that is recorded by the combustion condition detection device.
Be used to realize that combustion chamber equipment controller of the present invention has above-mentioned combustion condition detection system and one and is used to calculate flow velocity Effector by the flow velocity of the fluid (described fuel or described air) of Flow-rate adjustment valve regulation, this device is used for according to the measured combustion condition of the combustion condition detection device of combustion condition detection system control and supplies with at least a in the air of premix burner and the fuel, and exports the result to flow control valve.
To described in the description part of prior art, can carry out the estimation of certain program as the front to combustion condition according to the burning gas temperature of combustor exit.Yet the combustion gas at combustor exit place arrive the influence that is subjected to many factors in the process that exports after gas is by premixed combustion.Here it is why the burning gas temperature in outlet port always can accurately not indicate combustion condition.In contrast, if can directly measure the premixed combustion flame temperature, can accurately indicate combustion condition, yet, owing to there is not so high flame temperature of thermometer energy measurement, up to the present can provide a kind of device that detects combustion condition according to premixed combustion flame self also establishing.
For addressing this problem, the present invention is according to the temperature detection combustion condition of the stabilizer that is used for stablizing premixed combustion flame.Stabilizer is smooth combustion flame by survey the circulation that forms the combustion gas that result from premixed combustion in its downstream, keeps the downstream side temperature higher and light premixed gas at this place.Thereby stabilizer is exposed in the combustion gas that produced by premixed combustion, thereby can accurately indicate the premixed combustion flame temperature, and can accurately learn combustion condition from the stabilizer temperature.In addition, because the stabilizer temperature is starkly lower than the premixed combustion flame temperature, an in fact available thermometer is measured this temperature.
The present inventor has found to have certain relation between this stabilizer temperature and the air-fuel ratio, and this relation is one of sign of combustion condition.By means of this relation, can accurately learn the air-fuel ratio of premixed gas, with the air-fuel ratio of control premixed gas.
Stabilizer is stablized premixed combustion flame by form premixed combustion gas circulation in its downstream side, thereby stabilizer is exposed in the combustion gas that produced by premixed combustion.Therefore the present invention can measure the temperature of combustion gas immediately after combustion gas produce.Here it is, and why the present invention can accurately know combustion condition.
Fig. 1 is the cross-sectional view of the gas-turbine combustion chamber of first embodiment of the invention;
Fig. 2 is the perspective view of the stabilizer in one embodiment of the invention;
Fig. 3 (a) is to 3(d) respectively be the cross sectional view that helps a kind of form of the cross section of disturbing device;
Fig. 4 (a) is to 4(e) respectively for helping a kind of setting type of disturbing device;
Fig. 5 is the schematic representation that the thermal conduction characteristic of stabilizer is shown;
Fig. 6 is the cross-sectional view of the stabilizer in one embodiment of the present of invention;
Fig. 7 is the perspective view of the stabilizer in the second embodiment of the present invention;
The schematic representation that Fig. 8 concerns for the position that stabilizer shown in Figure 7 and premix chamber are described;
Fig. 9 is the cross-sectional view that the premix chamber of the stabilizer among the third embodiment is installed;
Figure 10 is the skeleton diagram that utilizes the waste-heat power generation system;
Figure 11 is the schematic representation of the stabilizer in the explanation fourth embodiment of the invention and the structure of stabilizer;
Figure 12 is the system schematic of the gas-turbine plant in the fourth embodiment of the present invention;
Figure 13 is the functional-block diagram of the controller in the fourth embodiment of the invention;
Figure 14 is the sectional view along IV among Figure 11-IV line;
Figure 15 is the sectional view along V among Figure 11-V line;
Figure 16 is the perspective view of the stabilizer in the fourth embodiment of the invention;
Figure 17 is the functional-block diagram of the controller in the fifth embodiment of the invention;
Figure 18 is the sectional view of the firing chamber in the sixth embodiment of the invention and the structure of firing chamber;
Figure 19 is the functional-block diagram of the controller in the sixth embodiment of the invention;
Figure 20 is the sectional view of the firing chamber in the seventh embodiment of the invention and the structure of firing chamber;
Figure 21 is the premix burner in the first embodiment of the present invention and the cross-sectional view of stabilizer;
Figure 22 is the premix burner in each different embodiment of the present invention and the cross-sectional view of stabilizer;
Embodiment 1
Fig. 1 illustrates one embodiment of the present of invention, and in the cross-sectional view of the gas-turbine combustion chamber that is equipped with stabilizer shown in Figure 1, stabilizer 11 is an annular.Burning is carried out in two combustion chambers 1 and 10, and in firing chamber 1, fuel and air carry out diffusive combustion.In firing chamber 10, fuel and air mix in a premix chamber 2 before burning, burn then to produce premixed combustion.The compressed distribution as requested of air in the gas compressor (this is not shown) is also sent into firing chamber 1 and the premix chamber 2 from air inlet 4 and 8 respectively.Air also is used for the cooling combustion locular wall, but omits the explanation to this purpose herein.Fuel is sent into firing chamber 1 and is sent into the premix chamber 2 by fuel nozzle 7 from fuel pipe 6 from fuel pipe 3 respectively.Stabilizer 11 is fixed on the outlet port in premix chamber 2 by supporting member 16.
Fig. 2 illustrates the part of the annular stabilizer 11 shown in Fig. 1.Stabilizer 11 comprises a flame holder (stabilizer part) 14 and a supporting portion 15 that partly links to each other with stabilizer, and it is a heat absorption surface that contacts with combustion gas that flame holder has this surface of combustion gas area of heating surface 13().Help and disturb device 12 and be installed on the surface except that the area of heating surface 13 of stabilizer 11.In this embodiment, stabilizer 11 is installed in the center of the outlet of premix chamber 2 as shown in Figure 1 with tabular supporting member 16.Also available other method of stabilizer is installed.
Fig. 3 (a) is to 3(d) example that helps the cross section of disturbing device 12 respectively is shown, Fig. 3 (a) illustrates rectangular cross section, and Fig. 3 (b) illustrates trapezoidal cross-section, and Fig. 3 (c) illustrates triangular cross section, and Fig. 3 (d) illustrates semi-circular cross-section.Disturb device with helping of any cross-sectional form; Effect of the present invention much at one.Each helps disturbs utensil and some ribs is as shown in the figure arranged with turbulent airflow.
Fig. 3 (a) also illustrates by around helping the exemplary of disturbing the streamline 20 that device 12 flow air and fuel forms.Form a vortex 21 in the downstream that helps machine 12.Disturb device when being arranged on the surface of stabilizer of a gas-turbine combustion chamber when helping, should be specifically noted that the size of this vortex 21.In other words, backfire is disturbed device 12 to helping if the change of the air stream that the flame that vortex 21, then only is formed at the area of heating surface 13 downstreams usually near the area of heating surface 13 among Fig. 2 causes owing to the variation by load makes progress.Its result will damage the firing chamber.The present inventor has found that, if according to the size that is formed at the eddy current 21 that helps the downstream of disturbing device 12 and air and the fuel flow rate set according to the operating range of gas-turbine combustion chamber, make helping of the most close area of heating surface 13 disturb distance between device 12 and the area of heating surface 13 itself for greater than helping 4 times of the height H of disturbing device, then can avoid this backfire problem, help the spacing of disturbing device to can be 5 to 10 times of height H, for example 10 times.If height H is 1mm or littler, than its for 1mm or when bigger heat conducting effect good, yet, if height H is 0.1mm or littler, then helps and disturb device and will cut little ice.
Fig. 4 (a) is to 4(e) be illustrated in respectively to be provided with on the surface of stabilizer 11 and help the example of disturbing device 12.In Fig. 4 (a), be provided with rectangular rib perpendicular to air stream and disturb device, this set is suitable for making stabilizer 11 with machining.For the stabilizer made from forging method, help and disturb device 12 and can as shown in Fig. 4 (b), favour air stream, be depicted as zigzag fashion as Fig. 4 (c), circumferencial direction branch along stabilizer 11 shown in Fig. 4 (d) is arranged, or along the circumferencial direction branch of stabilizer 11 be arranged and with air stream at angle.Like this, help machine 12 and air stream to be provided with at angle and separate with small distance by making, can improve as a purpose of the present invention from the transmission of heat of stabilizer 11 to air and fuel stream.
As Fig. 3 (a) to 3(d) and Fig. 4 (a) to 4(e) shown in help the shape of cross section of disturbing device 12 and be provided with and can freely determine according to the balance of easness two aspects of transmission of heat and manufacturing, be not limited to those shapes and the setting shown in the embodiments of the invention.
As mentioned above, the stabilizer among Fig. 2 11 comprises the stabilizer part 14 and the supporting portion 15 of a band combustion gas area of heating surface 13.Supporting portion 15 is parallel to air and becomes-30 ° or littler angle with fuel stream with the main flow of fuel stream or with air, and has enough length.Usually air and fuel stream quilt disturbance significantly, but in this case, be difficult to by helping machine 12 to quicken transmission of heat effectively.In this embodiment, air stream arrives stabilizer part 14 through rectification when the supporting portion 15 along stabilizer 11 flows.Help and disturb device 12 and be placed on supporting portion 15 and the stabilizer part 14.Yet,, will more effectively quicken transmission of heat because the temperature on the stabilizer part 14 is worked if helping on this section disturbed device 12 effectively than the height on the supporting portion.Can separate with stabilizer part 14 or be close to as the supporting portion 15 of rectifier and be provided with or be in contact with one another.Yet, as shown in Fig. 1,2, preferably supporting portion 15 and stabilizer part 14 are combined into one, in this case, can more effectively conduct heats to supporting portion 15, and the heat that supporting portion 15 ends also can more effectively be passed to air and fuel stream from the stabilizer part 14 that comprises the high temperature area of heating surface 13.
Angle φ between the area of heating surface 13 of known by experiment stabilizer 11 and the surface that is exposed to fuel and air stream of stabilizer part 14 is between 20 °-70 °, to stablize the burning in the gas-turbine combustion chamber.Fig. 5 illustrates angle theta between stabilizer part 14 and the supporting portion 15 and the relation between the maximum temperature on the stabilizer part 14.In cross section stabilizer 11 as shown in Figure 2, included angle is made as 45 ℃.From stabilizer 11 to fuel and the heat conduction efficiency of air stream determine by the heat conductivity transmission of heat them and the stabilizer 11.If Fig. 5 also illustrates the θ angle between 120 to 160 °, transmission of heat and heat conductivity obtain fine balance, and the calorific value maximum of conduction.Even the relation between the maximum temperature in angle θ as shown in Figure 5 and the stabilizer part when angle φ be one be not equal within 45 ° 20 °-70 ° angle the time also can be met.
Stabilizer also can have as shown in Figure 6 structure so that angle θ can be arranged between 120 ° to 160 °.In other words, the angle of the supporting portion 15 of close stabilizer part 14 makes it widen and be attached thereto towards stabilizer part 14.
According to present embodiment, help and disturb device and can guarantee that heat conducts to air and fuel stream from stabilizer.
Embodiment 2
Fig. 7 and 8 illustrates an alternative embodiment of the invention.Stabilizer 11 among this embodiment is not to be used for the annular premix chamber shown in Fig. 1, but is used for cylindricality premix chamber.Generally speaking, the shape of stabilizer resembles a pin as shown in Figure 7.It comprises that one has stabilizer part 14 and supporting portion 15 of an area of heating surface 13.Help and disturb device 12 and be arranged on the surface of the stabilizer part 14 of stabilizer 11 and supporting portion 15.The same with embodiment 1, help and disturb device 12 and can have as Fig. 3 (a) to 3(d) various shape of cross sections, and can be as Fig. 4 (a) to 4(e) freely be arranged on the stabilizer surface.The same with embodiment 1, the distance of disturbing between the device 12 and the area of heating surface 13 that helps of the most close area of heating surface 13 should be greater than helping 4 times that disturb the device height H, thereby make flame can backfire not disturb device 12 to helping, can be owing to the change of fluid that is caused by variations such as loads is damaged the firing chamber yet, and, help the height H of disturbing device 12 to should be 0.1mm to 1mm.
And, in the present embodiment, must make the angle φ that is exposed between the surface in fuel and the gas stream of the area of heating surface 13 of stabilizer 11 and stabilizer part 14 is 20 ° to 70 °, have this angle φ, then angle theta between stabilizer part 14 and the supporting portion 15 and the relation between the maximum temperature in the stabilizer are met as shown in Figure 5.Thereby the angle theta between stabilizer part 14 and the supporting portion 15 is preferably 120 ° to 160 °.The same with embodiment 1, the cross section of stabilizer can have structure as shown in Figure 6.In other words, can be angled near the supporting portion 15 of stabilizer 14, so that it is partly widened and is attached thereto towards stabilizer.
Fig. 8 illustrates with respect to premix chamber 2 and the stabilizer 11 that is provided with.Premix chamber 2 is arranged with ring and is separated by a distance mutually.Each stabilizer 11 can be fixed by support plate as shown in Figure 2, or fixes with any alternate manner, and the center circle among Fig. 8 is a control firing chamber.In this embodiment, helping of being mentioned among the embodiment 1 disturbed device and can be guaranteed heat conducting carrying out effectively, improving combustion stability, and prevents that the stabilizer local temperature is too high.According to present embodiment, help and disturb the stabilizer that device can be provided for having the gas-turbine combustion chamber of many premix chambers.
Embodiment 3
Fig. 9 illustrates the cross section of the stabilizer among another (3) embodiment of the present invention.Stabilizer 11 in the present embodiment is arranged on the inner circumference of premix chamber 2.The premix chamber can be illustrated in figure 1 as annular, or is illustrated in figure 8 as cylindrical.Certainly, the form of stabilizer changes according to the type of premix chamber.For annular premix chamber as shown in Figure 1, the stabilizer among this embodiment comprises two ring parts, an inner circumference that is arranged at inwall, and another is arranged at the excircle of inwall.For cylindrical premix chamber as shown in Figure 8, the stabilizer in the present embodiment comprises a ring part.
In a word, the stabilizer 11 in the present embodiment includes only stabilizer part 14, and omits supporting portion.Fuel in the present embodiment and air stream obtain rectification at the converging portion of stabilizer part 14, disturb device 12 and can guarantee to conduct effectively heat thereby be arranged at helping on the stabilizer.
And previous embodiments, lip-deep the helping that is arranged at stabilizer 11 disturbed device 12 and can be had as Fig. 3 (a) to 3(d) shown in any cross-sectional form, and can be as Fig. 4 (a) to 4(e) shown in freely be provided with.And previous embodiments, the distance of disturbing between device 12 and the heat absorption surface 13 that helps on the most close heat absorption surface 13 also should be greater than helping 4 times that disturb device 12 height H, and help the height H of disturbing device 12 to should be 0.1mm to 1mm, thereby make flame can backfire not disturb device 12 to helping, can be owing to damaging the firing chamber by caused change of fluid such as negative load variations.
If the angle between the surface of the inwall of premix chamber 2 and stabilizer is made as θ in this embodiment, then the relation between the maximum temperature on θ angle and the stabilizer will be as shown in Figure 5.Thereby the angle between the inner wall surface of the surface of stabilizer part 14 and premix chamber 14 should be preferably 120 ° to 160 °.The cone angle of stabilizer also can change in the neutral position to guarantee that angle θ is within 120 ° to 160 °.In this case, angle θ is not the inner wall surface of premix chamber and the angle between the stabilizer, but the angle between two crossing curved surfaces on formation stabilizer surface.
In the present embodiment, help and disturb the stability that device can guarantee that transmission of heat is burnt with raising, and prevent that the stabilizer local temperature is too high.In addition, according to present embodiment, can guarantee that stabilizer is fixed in the premix chamber, thereby can reduce the thermal distortion of stabilizer.
If of the present invention be equipped with the gas-turbine combustion chamber of deciding device with a kind of known mode with by gas turbine that results from the combustion gases drive in the gas-turbine combustion chamber and combinations such as gas compressor that link to each other with the turbine turns axle, the gas turbine that all is significantly improved in a kind of reliability and working life then can be provided.
If the gas-turbine combustion chamber that is equipped with stabilizer of the present invention with by the gas turbine that results from the combustion gases drive in the gas-turbine combustion chamber be used for combining by the generator that drives generation electric energy such as gas turbine, the gas-turbine power plant that all is significantly improved in a kind of reliability and working life then can be provided.
As shown in figure 10, if of the present invention be equipped with the gas-turbine combustion chamber of stabilizer with by the gas turbine that results from the combustion gases drive in the gas-turbine combustion chamber, be used for by driving the generator that gas turbine produces electric energy, the heat recovery boiler that produces steam with a heat that is used for by the combustion gas of discharging from gas turbine combines, and the system that utilizes the industrial waste heat generating that all is significantly improved in a kind of reliability and working life then can be provided.
The industrial waste heat power generation system of utilizing as shown in figure 10 has a gas turbine powered generator 30, it comprises a gas compressor 31, gas-turbine combustion chamber 40,41 and 42, one gas turbine 33 and a generator 34, one main boiler 50, one is used for supplying fuel charge device 35, one used heat of fuel 36 to utilize a boiler 60 and a cooling turbine unit 70 to gas-turbine combustion chamber and main boiler.
The combustion gas that produce in the gas-turbine combustion chamber 40,41 and 42 are admitted to gas turbine 33 to drive gas turbine and to produce electric power, are admitted to exhaust gas utilization boiler 60 then to produce steam.Steam is used for driving in summer cooling turbine unit 70, and is used for heating in winter.When this steam was not enough, the steam that results from the main boiler 50 was used for identical purpose.
Embodiment 4
Below, other various embodiments of the present invention are described.
At first, by Figure 11 to Figure 16 the fourth embodiment of the present invention is described.
As shown in figure 12, gas-turbine plant among the present invention is equipped with a gas compressor 150, a plurality of firing chambers 110 of use compressed air in gas compressor 150, gas turbine 160 by the combustion gases drive of from firing chamber 110, discharging, one generator 165 and by gas turbine 160 drivings is used to control the control gear 100 of these devices.
As shown in figure 11, each firing chamber 110 comprises a cylindrical combustion chamber housing 111, one forms the primary combustion tube 113 in a primary combustion chamber 112, one forms a secondary firing chamber 121 and is positioned at the secondary firing tube 122 in primary combustion tube 113 downstreams, one is used for fuel is sprayed into diffusion, the burner 114 in primary combustion chamber 112, one is used for the premix burner 123, that fuel sprays into secondary firing chamber 121 is used for the stabilizer 130 of the stable premixed combustion flame 129 that is formed by premixed combustion gas.
Diffusion burner 114 is arranged on the central axis of cylindrical combustion chamber housing 111.Primary combustion tube 113 also is positioned on the central axis of cylindrical combustion chamber housing 111, and is positioned at the downstream side of mixing burner 114, and a plurality of premix burners 123 are provided with around primary combustion tube 113 with circular pattern shown in Figure 14 and 15.As shown in figure 11, premix burner 123 has the unit, premix chamber 125 that a fuel nozzle 128 and is formed for the premix chamber 24 of fuel combination and air.Unit, premix chamber 125 has an air inlet 126 that is used for air is sucked housing 111 that is positioned at unit 125 upstream extremities.125 downstream is provided with an ejiction opening 127 that is used to spray premixed gas in the unit.Fuel nozzle 128 is arranged at the upstream of premix chamber 124.
Shown in Figure 11 and 16, stabilizer 130 comprises that stabilizer part 131 and that its cross section is almost an isoceles triangle shape is used to support the supporting portion 132 of stabilizer part 131.Its end face of stabilizer part 131(is towards upstream side, and its bottom surface is towards the downstream side) by supporting portion 132 at its bottom supporting, thereby make the bottom be positioned at the downstream of the ejiction opening 127 of premix burner 123.As shown in figure 15, stabilizer part 131 is the annular of stretching out at it corresponding to the upstream of a plurality of premix burners 123 of annular setting and the two ends of upstream side, thereby the premixed gas of ejection from premix burner 123 can be divided into inner circumference edge and outer periphery.Stabilizer 130 is fixing by a plurality of support plates 133 that are disposed radially in premix burner 123.Be embedded with a plurality of thermocouples 135 in stabilizer 130, as shown in figure 16, they are used to measure the temperature of the bottom (near the area of heating surface) of stabilizer part 131.Silver solder or nickel solder 134 are filled up in the hole that is used for being embedded thermocouple 135 in the stabilizer.The a plurality of firing chambers 110 that are used for gas turbine 160 form identical shape usually.Thereby preferably the thermometer of each firing chamber (thermocouple) 135 should be positioned at identical position so that corresponding mutually with the temperature of stabilizer.As shown in figure 11, these thermocouples 135 link to each other with the sensor 136 that is arranged at hull outside by signaling line.Signal passes through this sensor 136 and input controller 100.
As shown in figure 12, between gas compressor 150 and each firing chamber 110, air-pressure duct 151 is set.This conduit 151 is used for carrying pressurized air from gas compressor 150 to each firing chamber 110.This air-pressure duct 151 is provided with a thermometer 153 that is used to measure compressed air temperature, one is used to measure pressure meter 154 and flowmeter 152 that is used to measure air mass flow of air pressure, Air flow meter 152 can be a hot line mass flowmenter, one pitot tube flowmeter, one orifice meter, or the flowmeter of other type.Will be from thermometer 153, the signal input controller 100 of pressure meter 154 and Air flow meter 152.
As shown in figure 12, be used for comprising a main fuel combination pipe 171 to the fuel pipe of each firing chamber 110 transfer the fuels, many branch fuel combination pipes 174, these branch fuel pipes that come out from main fuel combination pipe 171 branches are used for mixing burner 114 fuelings to firing chamber 110, one main premixed fuel pipe 181, the many branch premixed fuel pipes 184 that are used for distributing premixed fuels that come out from main premixed fuel pipe 181 branches, and a plurality of premix burner fuel pipe that is used for distributing premixed fuels that comes out from minute premixed fuel pipe 184 branches to each premix burner 123 of a firing chamber 110 to each firing chamber 110.Yet, in Figure 11 to 13, omitted the premix burner fuel pipe.The fuel that distributes to each fuel pipe is identical.In the present embodiment, fuel is gas.At main fuel combination pipe 171, divide fuel combination pipe 174, be respectively equipped with fuel flow meter 173,176,183 and 186 on main premixed fuel pipe 181 and the branch premixed fuel pipe 184, and fuel control valve 172,175,182 and 185.The SC sigmal control of each fuel control valve 172,175,182 and 185 aperture origin self-controller 100, thereby the flow in each root pipe of may command.
As shown in figure 13, controller 110 comprises a plurality of abnormal combustion judging units 1101, is used for judging that according to the temperature that each measuring point at stabilizer is recorded by the thermocouple 135 that is located at firing chamber 110 burning is normal or unusual; Mean temperature computing unit 1102 is used for basis by a plurality of mean values that are arranged at combustion chamber thermocouple 135 temperature in the temperature computation stabilizer that measuring point records; An air-fuel ratio computing unit 1104 is used to calculate the mean value of the difference between the air-fuel ratio of average air-fuel ratio and each firing chamber 110; Divide premixed fuel amount computing unit 1107, be used for calculating the fuel quantity of supplying with branch premixed fuel pipe 184, and export its result to one fen premixed fuel modulating valve 185 according to the air-fuel ratio deviate of each firing chamber 110; Main premixed fuel amount computing unit 1108 is used for supplying with according to the external loading calculated signals fuel quantity of main premixed fuel pipe 181, and exports the result to main premixed fuel modulating valve 182; One waste gas NO xConcentration computing unit 1105 is used for calculating waste gas NO from average air-fuel ratio xConcentration; And a display unit 1109, be used to show the abnormal combustion judged result, the air-fuel ratio of each firing chamber 110, average air-fuel is waste gas NO when xConcentration etc.Except said apparatus, controller 100 also is equipped with a diffused fuel amount computing unit etc., is used to calculate the amount by the described diffused fuel of modulating valve 172,175 controls.
Be exactly the controller software structure of controller 100 above.In fact, in this embodiment, controller 100 constitutes a computer.Display device 1109 is made of display unit, and other is used for the parts of other function or unit and is made of the ROM and the RAM of storage data and program, and handles and carry out these data and program with a CPU.
Below, the operation of present embodiment is described.
The air that is used for burning is compressed at gas compressor 150, is transported to each firing chamber 110 by air-pressure duct 151 then.Portion of air is directly sent into primary combustion chamber 112, and part is admitted in the premix chamber 124 of premix burner 123 in the remaining air.In addition, some air is used to cool off primary combustion tube 113 and secondary firing tube 122(is not shown).On the other hand, by main premixed fuel pipe 181, be provided for each firing chamber 110 each minute premixed fuel pipe 184 and each premixed combustion organ pipe of being provided for each premix burner 123 fuel that will be used for premixed combustion send into the fuel nozzle 128 of premix burner 123.The fuel that is used for diffusive combustion is delivered to diffusion burner 114 by main diffusion fuel pipe 171 and the branch diffused fuel pipe 174 that is provided for each firing chamber 110.
Sending into air in the primary combustion chamber 112 and fuel spreads in this chamber and burns.The high-temperature combustion gas that is produced by this diffusive combustion enters primary combustion chamber 112 and is used for the stable premixed combustion flame 129 that is formed at this chamber.
Fuel nozzle 128 fuel that sprays and the air mixing of delivering to nozzle 128 from premix burner 123.Then, fuel is entered secondary firing chamber 121 from spout 127 ejection of premix burner 123, the combustion gas that produced by this burning are recycled into the downstream side of stabilizer 130, cause that stabilizer 130 downstream side temperature raise.Thereby form stable premixed combustion flame 129 in the downstream side of stabilizer 130.
The combustion gas that produce in each firing chamber are admitted to gas turbine 160 to drive this gas turbine.Then, this gas turbine drives generator 165.
The temperature of the stabilizer 130 that is recorded by thermocouple 135 exports controller 100 to by conveyer 136.This temperature signal is used to control premixed fuel.
To describe how to control premixed fuel below according to the temperature of stabilizer 130.
Combustion condition in each firing chamber 110 is represented by air-fuel ratio usually.The present inventor has found that the relation between the temperature of this air-fuel ratio and stabilizer 130 can represent to following equation roughly.In other words, owing to can go out air-fuel ratio from the temperature computation of stabilizer 130, thereby can learn combustion condition from the temperature of stabilizer 130.
T f=TO+K 1T a-K 2I n(λ) ... (equation 1)
T wherein f: the stabilizer temperature (℃), TO: constant (℃), T a: enter the air in the firing chamber 110 temperature (℃), K1: constant (-), K 2: constant (℃), λ: air-fuel ratio (-).
Constant is different and different according to the structure of operational condition and firing chamber 110.Thereby, be difficult to draw concrete temperature T fWith with respect to temperature T fAir-fuel ratio λ.Yet be an example below: if air-fuel ratio λ (λ=17.4) is theoretical air-fuel ratio, fuel is methane in this embodiment, in 29.6 to 33.1 scope, and the stabilizer temperature T fTo reduce about 30 ℃.
Air-fuel ratio λ and waste gas NO xRelation between the concentration can be represented with following equation roughly
NO x=K3-K4I n(λ) ... (equation 2)
Wherein, NO x: waste gas NO xConcentration (ppm), K3: constant (ppm), K4: constant (ppm), equation 2 is pointed out NO xRelation between concentration and the air-fuel ratio.When this equation is combined with equation 1, nature can obtain a definite NO xThe equation that concerns between concentration and the stabilizer temperature.
Controller 100 is checked the combustion condition of each firing chamber 110, to control premixed fuels with aforesaid equation 1 and equation 2.
Specifically will then, judge according to these signals whether combustion condition is normal from the signal input controller 100 that is located at the thermocouple 135 in each firing chamber 110 corresponding to the fuel abnormal deciding means 1101 of firing chamber 110.Whether the temperature according to stabilizer 130 is judged within lower limit that presets and CLV ceiling limit value.CLV ceiling limit value is the temperature that the material of stabilizer 130 allows, for example 840 ℃, lower limit deducts the value of regulation by the temperature from stabilizer 130, and for example 100 ℃ and obtain, the temperature of stabilizer is that the air-fuel ratio of appointment below certain load is calculated.
If the temperature of stabilizer 130 surpasses CLV ceiling limit value, then stabilizer 130 begins fusing, in the worst case, if the temperature that backfire stabilizer 130 takes place is surpassed lower limit, will exit.For preventing the generation of this situation, if any signal from the thermocouple in the firing chamber 110 135 indicates an abnormal temperature (surpassing preset reference temperature), to warning signal of main premixed fuel amount computing unit 1108 outputs closing main premixed fuel modulating valve fully, thereby stop to each firing chamber 110 fuel supplying.Main premixed fuel amount computing unit 1108 is usually according to the load signal computing fuel levels of outside, and exports the result to premixed fuel modulating valve 182 to control main premixed fuel amount.The fuel quantity that is independent of each firing chamber 110 owing to main premixed fuel amount (total premixed fuel amount) is by this way controlled, even thereby postpone or mistake when time of origin in the control of the fuel quantity of each firing chamber 110, also can prevent the change of generating electricity.
If combustion case is normal, in fact the temperature of stabilizer 130 exports mean temperature computing unit 1102 to, in this computing unit 1102.The calculating mean temperature that each measurement point records in stabilizer 130.Air-fuel ratio computing unit 1103 usefulness equations 1 are calculated the air-fuel ratio of each firing chamber by the mean temperature of stabilizer.Calculate for carrying out this air-fuel ratio, need to flow into the temperature T of the air in the firing chamber 110 a, this temperature value is obtained by the thermocouple 153 that is arranged in the air-pressure duct 151.Average air-fuel ratio computing unit 1104 calculates the mean value of the 110 air-fuel ratios that obtain from all firing chambers.Export this average air-fuel ratio to air-fuel ratio deviation calculation unit 1106, to calculate the deviation of air-fuel ratio in each firing chamber.Export this air-fuel deviation to branch premixed fuel amount computing unit 1107, to calculate the branch premixed fuel amount of each burning cavity that can eliminate this deviation.Yet in this case, the total value of the branch premixed fuel amount of each firing chamber 110 must be set as main premixed fuel amount (total premixed fuel amount), and the total value of main premixed fuel amount+main diffusion fuel quantity must be set to total fuel quantity.The branch premixed fuel amount of each firing chamber is exported the most branch premixed fuel modulating valve of each firing chamber setting, flow into the fuel quantity that divides in the premixed fuel pipe 184 to regulate.Average air-fuel ratio also is output to waste gas NO xConcentration computing unit 1105.Calculate waste gas NO with equation 2 by this average air-fuel ratio xConcentration.If result of calculation surpasses the preset upper limit value, then will export each air-fuel ratio deviation calculation unit 1106 corresponding to the average air-fuel ratio of this exceedance to be reduced to gas NO xConcentration.In addition, average air-the fuel ratio of subsequent calculations is greater than the air fuel ratio of calculating in the average air fuel ratio computing unit 1104 (amount of air is greater than the amount of fuel), and each air-fuel ratio deviation calculation unit 1106 calculates the deviation between the air-fuel ratio of these average air-fuel ratios that calculate recently and each burning cavity.
If detect abnormal combustion in any one fuel abnormal deciding means 1101, unusual firing chamber then takes place appear on the display screen 1109.This display screen is also exported the air-fuel ratio of each firing chamber, the average air-fuel ratio of institute's combuster 110 and waste gas NO xConcentration.
Owing to check combustion case according to the temperature of stabilizer 130 by this way in this embodiment, this method in fact temperature with the premixed combustion flame 129 of directly measuring the downstream side that is formed at stabilizer 130 is identical.Here it is, and why this method can accurately detect the premixed combustion situation.
If as shown in this embodiment for gas turbine provides a plurality of identical firing chambers, then because the foozle of each firing chamber, the length of pipe, the length of conduit etc., the combustion characteristic of each firing chamber is normally different.And if each combustion chambers burn rerum natura difference, then combustion gas (specifically, gas temperature and the NO that discharges from each firing chamber 110 xConcentration) characteristic is also different certainly.Therefore, the load that is applied on the blade of gas turbine 160 is inconsistent, thereby shortens the operating life of gas turbine 160 and increase the waste gas NO that discharges from partial combustion chamber 110 xAmount.This will cause the NO of discharge from institute's combuster 110 xThe increase of the mean value of amount.Yet, in this embodiment, the air-fuel ratio of each firing chamber is calculated, and the result is used to control the air-fuel ratio of each firing chamber, thereby make this value become the average air-fuel ratio of institute's combuster.But thereby the load of each fuel chambers of balance, to avoid the problems referred to above.
If waste gas NO xConcentration surpasses CLV ceiling limit value, and then average air-fuel ratio increases, thereby the air-fuel ratio of each firing chamber 110 can be controlled to be equal to average air-fuel ratio.Thereby can reduce waste gas NO xConcentration.
In this embodiment, be provided with a plurality of thermocouples 135 for firing chamber 110.This is used for accurately checking the combustion condition of each firing chamber 110.If do not need so accurately, then a thermocouple 135 can only be set in stabilizer 130.In this case, but save mean temperature computing unit 1102 in the slave controller.
In this embodiment, to the air-fuel of each firing chamber when average air-the fuel ratio of all firing chambers 110 calculate and show.Yet, because stabilizer 130 temperature self indicate combustion case, thereby can be by calculating the stabilizer mean temperature of institute's combuster 110 and do not calculate air-fuel ratio, and divide a premixed fuel according to the stabilizer mean temperature control of each firing chamber stabilizer mean temperature and institute's combuster 110 by the stabilizer mean temperature of each burning cavity.
Embodiment 5
Below, according to Figure 17 the 5th embodiment of the present invention is described.
This embodiment controls the combustion condition in the each several part in each firing chamber 110.The same with the 4th embodiment, be provided with a plurality of pre-burners 123 in the firing chamber 110.Each burner has a premix burner fuel pipe 187(and omits in Figure 13 of the 4th embodiment).Yet in the present embodiment, the premixed fuel of each premix burner 123 in the firing chamber 110 is supplied with in control.The branch premixed fuel amount of supplying with each firing chamber 110 is the same uncontrolled with embodiment 4.On premix burner fuel pipe 187, be provided with premixed fuel device fuel control valve 188.
Controller 100a comprises that one is used for judging in each firing chamber 110 whether normal abnormal combustion judging unit 1101 of burning according to the temperature of the stabilizer of being surveyed by the thermocouple 135 that is located at firing chamber 110 130, one be used for measurement point according to stabilizer 130 by a temperature computation that records in a plurality of thermocouples 135 at air-fuel ratio computing unit 1103a corresponding to the air-fuel ratio in the fuel region of temperature measuring positions, be used to calculate described average air-fuel ratio and corresponding to the air-fuel ratio deviation calculation unit 1106a of the deviation between the air-fuel ratio of the combustion zone of temperature sensing point, be used for the premix burner fuel quantity calculating unit 1107a of basis corresponding to the premixed fuel amount of each premix burner of air-fuel ratio deviation calculation of each fuel region of temperature sensing point, be used for main premixed fuel amount computing unit 1108 according to external loading calculated signals master premixed fuel amount, with be used to show the abnormal combustion judged result, corresponding to the display device 1109 of the air-fuel ratio of the fuel region of temperature sensing point and average air-fuel ratio etc.Except that display device 1109 and main premixed fuel amount computing unit, those functions of controller 100a are corresponding to each firing chamber.
The hardware configuration of present embodiment is except being provided with the premixed fuel modulating valve 188 for premix burner fuel pipe 187, the same with the 4th embodiment.
The following describes this embodiment's operation.When the signal of any entered controller 100a in from a plurality of thermocouples 135, abnormal combustion judging unit 1101 judged whether the fuel region corresponding to the temperature sensing point is normal in the stabilizer 130.Whether this judgement is the same with embodiment 4, then be to carry out above preset upper limit or lower limit by the temperature that detects stabilizer 130.If anyly indicate " exceeding predetermined temperature range " from the signal that is arranged at a plurality of thermocouples 135 in the firing chamber 110, then to abnormal signal of main premixed fuel amount computing unit 1108 outputs to close main premixed fuel modulating valve 182 fully and to stop to infeed fuel to institute's combuster 110.
If burning is normal, the air-fuel ratio computing unit 1103a air-fuel ratio of equation 1 calculating corresponding to each burning cavity of each combustion zone of each temperature sensing point of stabilizer 130.Average air-fuel ratio computing unit 1104a calculates the mean value corresponding to the air-fuel ratio of the temperature sensing point in the stabilizer 130.Export this mean value to each air-fuel ratio deviation calculation unit 1106a, to calculate and deviation corresponding to each regional air-fuel ratio of each temperature sensing point.Export this air-fuel deviation to each premix burner fuel quantity and calculate unit 1107a, calculating the premixed fuel amount of each premix burner, thereby eliminate this deviation.Export the premixed fuel amount of each premix burner the premixed fuel of premixed fuel device fuel control valve 188 to, thereby set this fuel quantity with adjusting inflow premixed fuel device fuel pipe 187.
As mentioned above, with the same among the 4th embodiment, the temperature of stabilizer 130 also is used to check the fuel situation in the present embodiment.Thereby, can accurately know the premixed combustion situation.In addition, because the fuel quantity of each premixed fuel device of may command, thereby, can make and in each fuel chambers 110, be easy to unbalanced fuel condition balance.
In Figure 17, the quantity of quantity of premixed fuel modulating valve 188 (quantity of=premix burner) and thermocouple 135 equates.This is for for the purpose of illustrating.For example, can be for 32 premixed fuel device fuel control valves in a firing chamber 110 only with 4 thermocouples 135.In this case, according to the temperature results that records by a thermocouple 135, with 8 premixed fuel modulating valve 188(=32/4) control premixed fuel.
This embodiment is used for controlling the fuel stream of a firing chamber 110 each premix burner 123.In order to regulate the premixed fuel stream of each firing chamber 110, controller 100a also can be provided with a single firing chamber air-fuel ratio computing unit 1103, an institute's combuster average air-fuel ratio computing unit 1104 that is used to calculate the average air-fuel ratio of institute's combuster 110 is used for the air-fuel ratio deviation calculation unit 1106 that average air-fuel ratio from each firing chamber air-fuel ratio and institute's combuster calculates the deviation of air-fuel ratio, with one be used for from the branch premixed fuel amount computing unit 1107 of the fuel flow rate of this air-fuel ratio drift indicator point counting premixed fuel pipe 184.
Embodiment 6
Below, with reference to Figure 18 and 19 explanations the 6th embodiment of the present invention.This embodiment is used for controlling to according to the temperature of stabilizer 130 air mass flow of each firing chamber 110b.
As shown in figure 18, firing chamber 110b in the present embodiment is provided with one and is used for measuring Air flow meter 141 and premix air-regulating valve 140 that is used to regulate described air stream of sending into the air mass flow that is used for premixed combustion in a premix chamber 124 from the air inlet 126 of each premix burner 123.Air flow meter 141 and premix air-regulating valve 140 are arranged at air inlet 126.Other burning cavity structure is the same with embodiment's 4.
Because the controller 110b among this embodiment is used for controlling according to the temperature of stabilizer 130 air-fuel ratio of each firing chamber 110b, it is the same basically with embodiment 4.Yet, this embodiment is used to control to the air mass flow of each firing chamber 110b when controlling the air-fuel ratio of each firing chamber 110b, thereby in the premix air quantity is calculated unit 107b, calculate the air mass flow that infeeds premix burner 123, and export this air quantity to premix air-regulating valve 140 according to the air-fuel ratio that in air-fuel ratio deviation calculation unit 110b, calculates.
In this embodiment, control flows into the air mass flow of each firing chamber 110, but the air-fuel ratio in each firing chamber 110 can be almost and fix, thereby present embodiment can obtain the effect identical with the 1st embodiment.
In the present embodiment, also provide a premix air-regulating valve 140, thereby can infeed air mass flow in each premix burner 123 with the same control among the embodiment 5 for each premix burner 123.
Embodiment 7
Below, with reference to accompanying drawing 20 explanations the 7th embodiment of the present invention.
This embodiment is the combination of aforementioned each embodiment's control.
In other words, present embodiment is used for dividing a premixed fuel modulating valve according to the temperature at the stabilizer of each burner by control, and premix burner fuel control valve and premix air-regulating valve are regulated the air-fuel ratio in each firing chamber and the air-fuel ratio of single firing chamber.This controller combines the function of the various embodiments described above.
According to present embodiment, can prevent the imbalance of air-fuel ratio in each firing chamber and the single firing chamber.Yet, owing to used so many various types of modulating valve in the present embodiment, thereby make present embodiment more unfavorable than the various embodiments described above aspect the manufacture cost and the problem frequency of occurrences.
In the various embodiments described above, measure the temperature of stabilizer 130 with thermocouple 135, but also can use other measuring device, for example, available resistance bulb replaces thermocouple, if resistance bulb can be measured the temperature of the temperature accepted of approximate stabilizer 130.
Stabilizer 130 in the foregoing description is a kind of so-called bluff stabilizers, the premixed gas separated into two parts that it will penetrate from premixed fuel device 123.The present invention also can use another kind of type-stable device.For example, a kind of so-called fluted body stabilizer 130a as shown in Figure 21, this fluted body stabilizer forms a combustion gas circulation in the downstream side of himself, and does not cut apart premixed gas.Stabilizer also can be the type shown in Figure 22, it around the spout 127b of premix burner 123b and the downstream of this nozzle form a combustion gas circulation.If adopt any among stabilizer 130a and the 130b, preferably the temperature of the corner of the stabilizer 130a/130b of the ignition point that will become premixed combustion flame 129 is measured.Blade is executed in label 145 expression whirlpools among Figure 21 and 22.

Claims (25)

1, a kind of gas-turbine combustion chamber stabilizer is characterized in that, is provided with a plurality of helping and disturbs device on the surface except that the heat absorption surface that contacts with combustion gas of stabilizer.
2, stabilizer as claimed in claim 1 is characterized in that, described help disturb the most close described heat absorption surface of being arranged so that of device help the distance of disturbing device and described heat absorption surface to be at least describedly to help 4 times that disturb the device height.
3, stabilizer as claimed in claim 1 is characterized in that, each described height of disturbing device that helps is in the scope of 0.1mm to 1mm.
According to the stabilizer of claim 1, it is characterized in that 4, described helping disturbed device along the circumferencial direction on described stabilizer surface separately.
According to the stabilizer of claim 1, it is characterized in that 5, described helping disturbed device and air stream inclination.
6, according to the stabilizer of claim 1, it is characterized in that, described stabilizer comprises a stabilizer part with described heat absorption surface, be arranged at the supporting portion of the upstream side of described stabilizer part with one with respect to air stream, and described supporting portion has the function that fuel and air stream are carried out rectification.
7, the stabilizer described in claim 6 is characterized in that, described supporting portion and described stabilizer part structurally structure are combined as a whole.
8, stabilizer as claimed in claim 7 is characterized in that, described supporting portion tilts, thereby the end of the close described stabilizer part of described supporting portion is partly widened towards described stabilizer.
According to the stabilizer of claim 6, it is characterized in that 9, described supporting portion becomes-30 ° or littler angle with main air flow.
10, stabilizer as claimed in claim 6 is characterized in that, the angle between described supporting portion and the described stabilizer part is in 120 ° to 160 ° scopes.
According to the stabilizer of claim 1, it is characterized in that 11, described stabilizer is an annular.
According to the stabilizer of claim 1, it is characterized in that 12, described stabilizer is a pin shape.
13, a kind of gas-turbine combustion chamber that is equipped with according to the described gas-turbine combustion chamber stabilizer of claim 1.
14, a kind of gas turbine engine that comprises gas-turbine combustion chamber as claimed in claim 13 is characterized in that also comprising that a gas turbine and by the combustion gases drive that produces is connected to the gas compressor on the rotatingshaft of described gas turbine in described gas-turbine combustion chamber.
15, a kind of power station that comprises the generator that drives by described gas turbine engine of gas turbine engine as claimed in claim 14.
16, a kind ofly comprise that gas turbine as claimed in claim 14 and one use the heat of the combustion gas of discharging to produce the system that utilizes the industrial waste heat generating of the boiler of steam from described gas turbine engine.
17, a kind of gas-turbine combustion chamber comprises:
One is used to spray the premix burner of the premixed gas of fuel and air;
One stabilizer is used in the circulation of the downstream side of described stabilizer formation by the burning combustion gas that described premixed gas produced, with the stable flame that is formed by the described premixed gas of burning;
Detect the device of the relation between the combustion condition described stabilizer and described premixed gas in advance; With
Be used to measure the device of described stabilizer temperature, check combustion condition with temperature and described relation according to measured described stabilizer.
18, gas-turbine combustion chamber as claimed in claim 17 is characterized in that, whether whether described relation indicate combustion condition normal in preset reference temperature according to the temperature of described stabilizer.
19, firing chamber as claimed in claim 17 is characterized in that, described relation is indicated the relation between the air-fuel ratio of a described burner temperature and a described premixed gas.
As the firing chamber of claim 17, it is characterized in that 20, described relation is indicated described stabilizer temperature and the NO in described combustion gas xRelation between the concentration.
21, a kind of gas-turbine combustion chamber comprises
One is used to spray the premix burner of pre-mixing gas combustion and air;
One stabilizer is used at the circulation of the downstream side of described stabilizer formation by the burning combustion gas that described premixed gas produced, with the stable flame that is formed by the described premixed gas of burning;
Be used to measure the stabilizer temperature measuring equipment of the temperature of described stabilizer; With
Be used for checking the device of combustion condition according to the relation between the combustion condition of the preset temperature of temperature that records by described stabilizer temperature measuring equipment and described stabilizer and described premixed gas.
22, firing chamber as claimed in claim 21 is characterized in that, also is provided with the device that is used to show by the detected combustion condition of described combustion condition detection device.
23, be equipped with the controller of combustion chamber equipment that a plurality of firing chambers and are used to regulate the valve of at least one fuel that flows into described premix burner and air, the premix burner of the premixed gas of ejection fuel and air is used in each firing chamber, with a stabilizer, this stabilizer is used at the circulation of the downstream side of described stabilizer formation by the burning combustion gas that described premixed gas produced, with the stable flame that forms by the described premixed gas of burning, wherein, controller has the device of the temperature of the described stabilizer of a measurement, one according to by the device of the measured temperature detection combustion condition of described stabilizer temperature measuring equipment, and one is used for calculating by the flow of described flow control valve modulating valve regulated fluid (described fuel and described air) and the result is exported to the device of described flow control valve.
24, according to the controller of claim 23, it is characterized in that, described combustion chamber equipment has a plurality of firing chambers and a plurality of flow control valve corresponding to described firing chamber, and described stabilizer temperature measuring equipment can be measured the temperature of the described stabilizer of each described firing chamber, and described combustion condition detection device has the function according to the combustion condition of each firing chamber of temperature detection on the described stabilizer, described flow computing device can calculate the flow by each described fluid of described Flow-rate adjustment valve regulation, and exports the result to described flow control valve.
25, controller according to claim 23, it is characterized in that, described firing chamber has a plurality of premixed fuel devices and a plurality of flow control valve corresponding to described premix burner, described stabilizer is arranged to stablize the combustion flame of the premixed gas of being supplied with by described a plurality of premix burners, described stabilizer temperature measuring equipment can be measured temperature on a plurality of points on the described stabilizer, described combustion condition detection device can be according to the temperature detection of each point on the stabilizer combustion condition corresponding to each combustion zone of the thermometry point on the described stabilizer, described flow computing device can calculate by corresponding to the flow of influence at each fluid of the described Flow-rate adjustment valve regulation of the described premix gas burner of the combustion condition of each combustion zone, and the result is outputed to corresponding flow control valve.
CN94104611A 1993-04-07 1994-04-07 Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer Expired - Lifetime CN1128951C (en)

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Application Number Priority Date Filing Date Title
JP80613/1993 1993-04-07
JP80613/93 1993-04-07
JP5080613A JP2798338B2 (en) 1993-04-07 1993-04-07 Gas turbine combustor and gas turbine engine
JP233393/1993 1993-09-20
JP23339393A JP2860234B2 (en) 1993-09-20 1993-09-20 Gas turbine combustor combustion control method and gas turbine combustor equipment for performing the method
JP233393/93 1993-09-20

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